Icephobic vane for a compressor of an axial turbine engine

Patent metadata

Field	Value
Publication number	US-10907488-B2
Application number	US-201716469789-A
Country	US
Kind code	B2
Filing date	Nov 8, 2017
Priority date	Dec 15, 2016
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.

First claim

The invention claimed is:

1. A vane for a turbine engine, the vane comprising:
a trailing edge;
an icephobic surface forming a leading edge of the vane; and
a hydrophobic surface extends from the icephobic surface towards the trailing edge.

2. The vane according to claim 1 , wherein the hydrophobic surface is an extrados hydrophobic surface.

3. The vane according to claim 1 , wherein the hydrophobic surface is an intrados hydrophobic surface.

4. The vane according to claim 1 , wherein the hydrophobic surface is an extrados hydrophobic surface;
wherein the hydrophobic surface is an intrados hydrophobic surface; and
wherein the extrados hydrophobic surface extends axially more than the intrados hydrophobic surface.

5. The vane according to claim 4 , wherein the icephobic surface connects the extrados hydrophobic surface to the intrados hydrophobic surface.

6. The vane according to claim 1 , further comprising:
an extrados side and an intrados side;
wherein the icephobic surface extends more on the extrados side than on the intrados side.

7. The vane according to claim 1 , wherein the icephobic surface extends over more than half of the thickness of the vane.

8. The vane according to claim 1 , wherein the vane comprises:
a zone upstream of the trailing edge, the zone having a roughness, and the hydrophobic surface having a roughness;
wherein the roughness of the zone is greater than the roughness of the hydrophobic surface.

9. The vane according to claim 1 , wherein the icephobic surface comprises:
nano-reliefs, such as nano-pillars and/or nano-cones.

10. The vane according to claim 1 , wherein the hydrophobic surface has a center line average roughness of less than 0.10 μm.

11. The vane according to claim 1 , wherein the hydrophobic surface comprises furrows.

12. The vane according to claim 11 , wherein the furrows are connected by bulges.

13. The vane according to claim 1 , wherein the icephobic surface contacts the hydrophobic surface.

14. The vane according to claim 1 , wherein the vane is made of titanium or aluminum alloy.

15. The vane according to claim 1 , wherein the icephobic surface comprises:
an anodized coating and/or a polymer coating.

16. A vane for a turbine engine, the vane comprising:
a trailing edge;
an icephobic surface forming a leading edge of the vane; and
a hydrophobic surface;
wherein the icephobic surface has a maximal sheer stress with ice and the hydrophobic surface has a maximal sheer stress with ice, and wherein the maximal sheer stress with ice of the icephobic surface is lower than the maximal sheer stress with ice of the hydrophobic surface.

17. The vane according to claim 16 , wherein the maximal sheer stress with ice of the icephobic surface is below two times less than the maximal sheer stress with ice of the hydrophobic surface.

18. The vane according to claim 16 , wherein the maximal sheer stress with ice of the icephobic surface is below ten times less than the maximal sheer stress with ice of the hydrophobic surface.

19. A vane for a turbine engine, the vane comprising:
a trailing edge;
an icephobic surface forming a leading edge of the vane; and
a hydrophobic surface;
wherein the vane is void of hydrophobic surface at least in a downstream half of the vane.

Assignees

• Safran Aero Boosters Sa

Inventors

• De Vriendt Olivier
• Raimarckers Nicolas

Classifications

• F01D25/02 Primary

  De-icing means for engines having icing phenomena · CPC title

• F05D2300/512

  Hydrophobic, i.e. being or having non-wettable properties · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2250/63

  coarse · CPC title